航天器的快速有限时间事件触发姿态跟踪控制  

Fast finite-time event-triggered attitude tracking control of spacecraft

作　　者：赵昕楠 高闯[1] 邹凌伟 杨永辉[1] ZHAO Xinnan;GAO Chuang;ZOU Lingwei;YANG Yonghui(School of Electronic and Information Engineering,University of Science and Technology Liaoning,Anshan 114051,China)

机构地区：[1]辽宁科技大学电子与信息工程学院,辽宁鞍山114051

出　　处：《安徽大学学报（自然科学版）》2023年第2期59-65,共7页Journal of Anhui University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(62173029)。

摘　　要：基于航天器姿态的最优控制律,将采用快速有限时间控制和固定阈值事件触发机制相结合,设计快速有限时间事件触发姿态跟踪控制器.仿真实验结果表明:在事件触发机制下,控制信号触发后呈阶梯变化,明显降低了信号的更新频率,节省了通信资源;航天器系统没有出现芝诺现象;相对于文献(丁世宏,李世华.基于四元数的空间飞行器姿态控制[C]//第25届中国控制会议论文集(上册),2006:283-287)的控制器,该文控制器能以更短的时间减小角速度误差,使航天器系统更快地达到稳态.Based on the optimal control law of spacecraft attitude,a fast finite-time eventtriggered attitude tracking controller was designed by combining fast finite-time control and fixed threshold event-triggered mechanism.The simulation results showed that under the event-triggered mechanism,the control signal showed a step change after triggering,which significantly reduced the update frequency of the signal and saved the communication resources.There was no Zeno in the spacecraft systems.Compared with the controller in literature(Ding Shihong,Li Shihua.Spacecraft attitude control based on quaternion[C]//Proceedings of the 25th Chinese control conference(volume I),2003:283-287),the controller designed in this paper could reduce the angular velocity error in a shorter time and make the spacecraft system reach the steady state faster.

关 键 词：航天器 姿态跟踪 快速有限时间 最优控制 事件触发机制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]